120
5 Supersonic Wind Tunnels
Fig. 5.6 Two-dimensional planar nozzle for a Mach 2.5 flow as a network of characteristics
Fig. 5.7 Mach 2 nozzle of S5Ch wind tunnel at ONERA, Meudon (© ONERA)
downstream by the characteristics starting from the nozzle extremity (see Fig. 5.8).
This volume is more extended in length as the Mach number is increased.
In most facilities, the Mach number is changed by replacing the upper and/or
lower blocks (wall liners) in two-dimensional configurations or the entire nozzle in
the axisymmetric cases. A rarer solution consists of designing a nozzle with walls
made of a flexible steel sheet, the Mach number being changed by deformation of
the wall by jack mechanisms. This solution is adopted in the S3MA wind tunnel at
the ONERA Modane-Avrieux centre (see Sect. 5.3.4).
5 Supersonic Wind Tunnels
Fig. 5.6 Two-dimensional planar nozzle for a Mach 2.5 flow as a network of characteristics
Fig. 5.7 Mach 2 nozzle of S5Ch wind tunnel at ONERA, Meudon (© ONERA)
downstream by the characteristics starting from the nozzle extremity (see Fig. 5.8).
This volume is more extended in length as the Mach number is increased.
In most facilities, the Mach number is changed by replacing the upper and/or
lower blocks (wall liners) in two-dimensional configurations or the entire nozzle in
the axisymmetric cases. A rarer solution consists of designing a nozzle with walls
made of a flexible steel sheet, the Mach number being changed by deformation of
the wall by jack mechanisms. This solution is adopted in the S3MA wind tunnel at
the ONERA Modane-Avrieux centre (see Sect. 5.3.4).